MPC based static aeroelastic numerical method for high aspect ratio wing

The steady aerodynamic loads were calculated with N-S equations and the multi-block structured grid technique was used to improve the computational efficiency. A beam model was applied to a high aspect ratio wing, and its structural deformations were evaluated by the finite element method with or without geometry nonlinearity. A multi-point constrain (MPC) method was used for the information exchange between the aerodynamic loads calculations and the structure deformations calculations. The static aeroelasticity was further considered. By successive iterations between self-developed computational fluid dynamics (CFD) solver and NASTRAN computational structural dynamics (CSD) software based on the MPC interpolation method, a quick and accurate coupled CFD-CSD method was achieved for the nonlinear static aeroelastic problem. Obviously the present method is more accurate than the conventional flexibility approach only considering single-direction deformation. Numerical analysis of a high aspect ratio wing demonstrates that spanwise deformation would have certain influence on its static aeroelastic characteristics and that geometric nonlinearity has small effect on this common airliner wing.